Airfoil simulation (NACA 2415)

- November 17, 2020 at 3:57 pm
  
  MTayyab
  Subscriber
  
  Hi,
  i am trying to do a flow over an airfoil simulation at different angles of attack.
  I have created the mesh, and for the inlet velocity at different angles of attack i input the correct velocity components my domain is c type domain but when i calculate the lift and drag coefficients i get very small values.
  My free stream velocity is 210m/s and at 4 deg angle of attack i get the following values:
  cd:
- November 17, 2020 at 4:02 pm
  
  Rob
  Forum Moderator
  
  Have a look in help as there's a video going through the NACA airfoil set up. Errors in the lift and drag are often caused by poor mesh, incorrect reference values or Force monitor vectors. n
- November 24, 2020 at 9:13 am
  
  Federico2594
  Subscriber
  
  Try to use the K-W SST model that is better for Airfoil Study.nIs important to keep the correct value of y+ to solve correctly the bundary layer.nRegards,nnFedericon

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